ENGINEERING RESEARCH INSTITUTE UNIVERSITY OF MICHIGAN ANN ARBOR BIMONTHLY PROGRESS REPORT NO. XIV THERMAL-SHOCK INVESTIGATION By T. A. HUNTER L. L. THOMAS A. R. BOBROWSKY Project M949 WRIGHT AIR DEVELOPMENT CENTER, U.S. AIR FORCE CONTRACT AF 33(038)-21254, E. 0. No. 605-227 SR 3a January, 1954

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ENGINEERING RESEARCH INSTITUTE * UNIVERSITY OF MICHIGAN BIMONTHLY PROGRESS REPORT NO. XIV THERMAL-SHOCK INVESTIGATION OBJECT The object of this research is to evaluate optimum design of test specimens and to develop criteria which will permit correlation of thermalshock data with performance of the material in the form of turbine buckets. SUMMARY I I. I Construction of the operating units for the four new testing rigs has been completed. Calibration tests must still be made, and the automatic camera equipment installed. Tensile tests have been run on H.S. 21 material to check the effects of aging at 1350~F for 50 hours. Tests at room temperature verify published data for the as-cast condition, but for the heat-treated condition the observed figure of 7.2 percent elongation differs considerably from the published figure of 1.7 percent. Tests have been completed on Inconel at temperatures of 1900 and 20007F. At these temperatures this material fails rapidly, crack detection is difficult, and scale formation is severe. For these reasons the scatter of the results is greater than usual. 1

ENGINEERING RESEARCH INSTITUTE ~ UNIVERSITY OF MICHIGAN INTRODUCTION As stated in previous progress reports, construction of new testing facilities has been under way since May, 1953. This construction program has increased the testing facilities from one active and one standby assembly to five active and one standby unit. The standby unit is now used for calibration purposes only, but can be made active if it is needed.. The new units have been checked out both mechanically and electrically and found to operate in a satisfactory manner. Completion of the units requires attention to a few nonoperating details, such as soundproofing and calibrating. Following the calibration procedure, a series of reproducibility tests will be run to make certain that the data obtained from the new machines will be the same as those obtained from previous tests on the old equipment. The outstanding feature of the new equipment is that it is praco tically automatic in operation. An automatic camera is to be installed on each unit to make a record of the condition of the specimen at chosen intervals; this record will permit running tests during the night without attendance. In Progress Report XI it was reported that tests had been run to determine the effect of change in ductility on the thermal-shock properties of H.S. 21 (cast Vitallium). Tensile tests have been run at room temperature to find the amount of change in ductility which has been produced by aging the material for 50 hours at 13500F. A graphical presentation of the data obtained is given in Fig. 1. These data are to be compared with the published information from the alloy manufacturer.1 The manufacturers state that for the as-cast condition, a room-temperature test will show a tensile strength of 101,300 psi and a percentage elongation of 8.2. It would appear that the observed tensile strength is only slightly below the published figure, and that the elongation is very close to the Haynes value, It is to be noted that none of the Haynes tables give any probable errors, and none of the graphs show any plotted data points. An exact comparison is thus rendered difficult. For the heat-treated condition the difference between the observed and the published data for the tensile strength is within the limit of the '"Haynes Alloys for High-Temperature Service", Haynes Stellite Companry, p. 9, 11. 2

15 14 KPSI 150[ 140 14.3 I I% 13.4 131 130o 12 120 IlI 1 10 Io 10oo0 92.9 c% L Z2 0 48 z o0 w7 z L6 C) 4 3 2 0 r 901 - I *80 z w -cr"-70 -J (I) w z w +-50 11.2 101.5 101.7 95. 9.2 77 7.6 F 0 124 122 12I 12c J 40~ 30[ 713 8.i / 13.8 98 FIG.I TENSILE TEST OF HAYNES STELLITE NO. 21 (VITALLIUM ).,g., 8.6 i I TENSILE STRENGTH PERCENT ELONGATION 7.2 201 2.8 o 0 - I 6 ---A L ---j L ----i,, I I Ia jLr II A - SPEC. NO. 2 4 7 17 ( AS CAST ) 22 19 16 12 (AGED 50h R 1350eF) AV., AS CAST - a. AV. AGE6

ENGINEERING RESEARCH INSTITUTE ~ UNIVERSITY OF MICHIGAN observed probable error. However, the values for the observed elongations compare poorly with the published figure of 1.7 percent. In no case was the observed percentage elongation less than 2.8, and one test showed 13.8 percent. At the request of Wright Air Development Center, thermal-shock tests have been run on Inconel at temperaturesbeyond those normally expected. Previous testshad been run at temperatures as high as 1800~F, but the new series was performed at 1900~ and 2000~F. As expected, the thermal-shock properties of the material deteriorated. However, any exact correlation with previous data on tests at the lower temperatures would be of doubtful value in view of the fact that the shape of the specimen has been changed since the early tests were performed. A complete set of tests on Inconel is scheduled for the near future. This work was performed in the period October 12, 1953, to December 12, 1953. APPARATUS AND PROCEDURE Tests to measure the ductility properties of H.S. 21 were carried out in a standard tensile testing machine of 120,000-pound capacity, but using the 12,000-pound range. The specimens were made up from 1/2-inchdiameter bars which had been machined down to a 1/4-inch diameter in the test section. The ends of the test pieces were threaded to be held in holders All gauge lengths were made 1 inch. These pieces are the usual ones for this type of work. Since H.SQ 21 is such a hard material, no gauge punch marks could be made in its surface. In order to get gauge marks from which to work, the surface was painted with lay-out blue and marks were scribed in the blue coating. It is to be noted that no preliminary x-ray tests were made to certify the soundness of the cast pieces. After being pulled, the two halves of the broken piece were placed together in the mating position again. The distance between the scribed gauge lines was then measured with an optical comparator in order to get the gauge length after testing. The difference between the final and the initial distan-es between the gauge lines was taken as the amount of elongation in 1 inch. It is to be noted that in some cases the two pieces fitted back together in a very neat manner, but in some other cases the edges of the fracture were so rugged that a close fit was impossible to obtain. It is felt that, in a few cases at least, the error involved in the measurement of the broken length must include a comparatively large gap between the two pieces. Two typical fractures are shown in Fig. 2.

Fig. 2. Fracture on left can be mated easily to give an accurate measure of elongation. Fracture on right cannot be mated accurately. 5

ENGINEERING RESEARCH INSTITUTE * UNIVERSITY OF MICHIGAN The data on these specimens are given in Table I. TABLE I Average Tensile Thermal- Average Condition Specimen Tnsil Percent Thermal- Tensile Average Condition Strength Shock Percent No. Is i Elongation Strength N.Eogpsi Cycles Strength Elongation psi ''., '., " 1 c..,-,,,,1 As -cast 2 92,900 11.2 4 95,900 7 101,500 17 101,700 2.2 7.6 13.4 3552 6820 1506 98,000 +2, 520 8.6 + 2.9 3279 J Aged 50 hours at 1350~F 22 19 122,000 124,000 4.3 8.1 18,411 10,060 129,500 7,2 + 4.2 +5,530 16 129,000 12 143,000 13.8 2.8 7375 J The testing of Inconel at elevated temperatures was carried out on a series of nine specimens. Five were run at 2000~F and four at 19000F. In each case the heating and cooling cycles were maintained at 50 seconds and 5 seconds, respectively, as in previous work. Considerable difficulty was experienced in conducting these tests because of the formation of large amounts of heavy surface scale on the specimen. In almost every case the scale was so heavy, rough, and fissured that there appeared to be a crack in the specimen, but on examination after the specimen was removed from the test stand the crack became questionable. The data reported in Table II are subject to confirmation by metallographic examination. 6

ENGINEERING RESEARCH INSTITUTE ~ UNIVERSITY OF MICHIGAN TABLE II DATA ON INCONEL, LOT II (1/2" D. H. Ro ROD) Cycle Specimen No. Cycles to Failure Type of Failure Remarks -- -- -- — ~ --— ~- --- ---- -- - - -- -- -- -- -- ~ -- -- 2000/5 958 -398 C 2000/5 2000/5 2000/5 2000/5 B5 B6 C? C? 212 (1) (2) (2) (2) (2) B7 299 C? B12 C? 1900/5 1900/5 1900/5 1900/5 B13 58o + C o.6 B14' O? (3) (2) (2) (2) -j B15 659 C? 0? B16 175 (1) This test was continued until a clear indication of failure was obtained. The resulting crack was far over the end-point, as previously defined. (2) These tests were stopped as soon as indications of failure were noted. After removing the specimen, the cracks were no longer visible, owing to heavy scale formation which is extremely rough and fissured. These failures are therefore considered questionable, pending metallographic examination. (3) This test was clearly incomplete, the crack extending only o.6 of the way across the edge land. It is impossible to determine the true number of cycles to failure because of the erratic nature of the crack propagation. 7

I iI I i i i I ENGINEERING RESEARCH INSTITUTE ~ UNIVERSITY OF MICHIGAN DISCUSSION OF RESULTS The comparatively large probable errors in the measurement of the elongation of the H.S. 21 cast specimens may be laid to two primary causes: the nature of the fracture surfacer which prevents an accurate measurement of the broken length, and the existence of shrinkages in the specimens. It is understood that vanes, buckets and blades used in aircraft turbines are subject to a 10 x-ray inspection when made from H.S. 21 material. This inspection is made primarily to find shrinkages, but it was not used on the test pieces for the elongation experiments. We have been advised by Haynes to have such tests made, and will report on them in the future. In any event, a probable error which is larger than some of the values recorded makes the data subject to suspicion. Examination of the percentage elongation and thermal-shock cycles to failure shows little, if any, relationship between them. The tensile' strength and thermal-shock cycles appear to be related in direct proportion: 30 percent increase in the tensile strength corresponds to an increase in thermal-shock resistance of about 400 percent. CONCLUS IONS 1. The thermal-shock resistance of Inconel deteriorates at temperatures of 1900~F and 20000F. Exact comparisons with lower temperatures depend on future data. 2. On the basis of available tenuous data, the ductility of cast 11S. 21 (Vitallium) alloy does not have an appreciable effect on thermalshock resistance. The tensile strength does, however, appear to have a pronounced, directly proportional, effect on the thermal-shock resistance. 8

I ENGINEERING RESEARCH INSTITUTE UNIVERSITY OF MICHIGAN - nEY TO LOG Column (1) (1) Relative position on bar stock 1 Specimen number Column (2) w.045 P.F.. x 1700/5 (1718) Arrow indicates direction and location of cooling Jet; cooling medium is air unless otherwise stated Cooling medium is water Width of cooled edge, inches Previously subjected to rotating beam fatigue as shown in column (6) Failed during pre-fatigue Number in parentheses indicates average of calibrations at beginning and end of test (Mean max test temp) Column (3) - M Thermal shock cycle manually controlled 1500/5 Autamatic cycle control; maximum temperature, OF, and length of cooling period, Seconds P1800 Dead load, 1800 lbs +10/100 Starting with stated maximum temperature, maximum temperature was increased 10~F after each 100 cycles 40.5E Reversed-bending (rotating-beam) fatigue tests; maximum stress, 40,500 psi to 1800 Maximum temperature held constant after 18000F was reached Column (4) A W no symbol Column.:(5) 0' F C G FC PC Column (6) B A 0.14 T300/1600 G1500 Air cooling for stated number of cycles Water cooling for stated number of cycles Air cooling for stated number of cycles No failure visible Fracture Cracks Grooves. Face crack Possible crack Specimen warped due to thermal strains Area of cross section, square inch Heat treated before testing 300 hr at 1600~F. Grooves first appeared at 1500 cycles A-1

-- ENGINEERING RESEARCH INSTITUTE ~ UNIVERSITY OF MICHIGAN pf 1700/6 V1200/2 40.5 82c +100/51 JCheckLR T e c20/17 Column - ( Column ( OH Stated maximum temperature was exceeded due to malfunction of control unit BT Broke through to thermocouple hole O) Previously subjected to cyclic heating and cooling {J (Max temp) 1700/60 (Heating time, seconds) (Min temp) 1200/23 (Cooling time, seconds) (Number of cycles) 1000 O0K/ Previously subjected to 82000 cycles at 40,500 psi )00 R Reproducibility test N Specimen formed a neck due to tensile strain..08 Maximum temperature was increased 1000F at 5108 cycles. _TI Second test to determine the effect of alteration of testing procedure; P Study of crack propagation )T1 Previously subjected to tensile strain of 1% at room temperature,SI Long-time test at reduced severity, Test No. I )I Heat treated as shown in braces (. Lot No. I 700 Heat treated for 20 hours by heating to 17000F and allowing to cool for 5 seconds by natural convection. 2) Letter at tail of arrow indicates test unit on which test was run. Two arrows indicate two separate tests with cooling on different edges. Horizontal arrow indicates first test 3) Number [e.g., (1)] indicates edge number, shown in Column (2), on which test was run. A-2

TEST LOG Specimen Cross Number Type of Remarks Number Section of Cycles Failure (1) (2) (3) (4) (5) (6) Type 304 Stainless Steel M 0 B I2~.045 2 1600/10 4400 A C B I I '....I III, I300W 3 16Q0/4 1783 C 4a Fatigue 40.5k 3300 F 4b Specimens 40.5K 2600 F 5 1700/4 1100 0 1800/4 675 C 6 1600/4 '6240 0 G65OO 1900/4 '124o C 7 Q 1500/4 4130 F A 0.16 P600 1'~ ~o A-3

TEST LOG (cont) Specimen Number (1) Cross Section (2) Cycle (3) Numbe.r of Cycles (4) Type of Failure (5) Remarks (6) ~~~~~~~~~~~~~~~~~~~~, _., ii i _I - -- _ i TSype 304 Stainless Steel (cont) 8 9 16o0/5 1800/4 3082 517 0 C T300/1600..,...._.....r,!,.!, Il 9 1500/3 5753 ~ I *.;I. I. i I E l_' ", ll,~I.... l.J..._ 16oo/4 1000 o 10 o 170o/4 1000 0 _ _ 180o/4 80 C J. 11,.~.!.. '. l _I, l.l,.. 11 4, 9 1500/5 P1800 1000 F A 0.132 A 0.133 12 4, 1500/5 P600 P900 P1800 5000 1200 203 0 0 F u ~ ~~~~~~~ ~ ~ ~ ~ ~ ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ i!..i... 13 1 16o-o/4 1284 C G115 13 _ I I... " 14 -Ao 1500/4 00ooo F OH

TEST LOG (cont) Specimen Cross Number Type of Remarks Number Section of Cycles Failure (1) (2) (3) (4) (5) (6) Type 304 Stainless Steel (cont) 15 1600/5 1900 C T300/1600 16 - 1600/5 409 C 17? 1500/5 300 F A 0.140 P1800 18 1800/4 1950 C G 1500 19 v 1700/3 530W C 20 1500/3 1000 0 BT.~ 1 500/.. 3.. A-5

TEST LOG (cont) Specimen Cross Number Type of Remarks Number' Section of Cycles Failure (1) (2) (3) (4) (5) (6) Type 347 Stainless Steel 1.045 1600/4 866 C +10/100.045 2 1600/4 1147 C.020 +/100 3 K 1500/4 575 C BT +10/100 4a Fatigue 54K 5200 F 40.5K 4b Specimens 54K 10400 F 82000 5' 1500/4 1326 +10/100326 C 2K7 1500/4 1990 C +10/100 ~ 1600/3.5 7 +10/100 2700 G to 1800 A-6

TEST LOG (cont) Specimen Cross Cycle Number Type of Remarks Number Section of- Cycles Failure (1) (2) (3) (4) (5) (6) Type 347 Stainless Steel (cont) 8 (Defective) 9 \0 _ 1600/4 2863 C R >.035 10 1600/4 3787 C Check II ->.020 11 1600/4 2580 C +.050 12 1600/4 3162 C G 736.020 13 7 1600/4 2204 C G 2072 >.020 14 0 1600/4 2707 C G 2604.020 A-7

TEST LOG (cont) Specimen Cross Cyle Number Type of Rerks Number Section of Cycles Failure (1) (2) (3) (4) (5) (6) Type 347 Stainless Steel (cont) 15 1600/4 3003 C G2820 V.035 R 16 1600/4 2518 C R.020 17 1600/4 4850 0 Check I.023 18, Fatigue 7200 F 54K 64K 103300 19 \7 1600/4 1825 C R o35 37K/217100 42K/11000 20 Fatigue 4300 F 48K/35600 V 64K 54K/10000l 59K/10400 21 1600/4 4430 C A-8

TEST LOG (cont) Specimen Cross Cycle Number Type of Remarks Number Section Cycle of Cycles Failure (X) (2) (3) (4) (5) (6) Type 347 Stainless Steel (cont) 22 (Defective) 23 1600/5 2962 C 24 Fatigue 52900 F ~V ~ 59K.010 25 1600/5 1562 C 54K/50000 ~V ~ P.F..010 53K/52000 59K/12000 26 1600/5 1960 C 64K/10oo 70K/1000 -.010 75K/500 27 X F 53K/52000 P.F. 59K/11300.010 53K/52000 59K/12000 28 \77 1600/5 1594 C 64K/1000ooo V P.F. 70K/1000 4.010 75K/500 A-9

TEST LOG (cont) Specimen Cross Number Type of Re rk Number Section of Cycles Failure (1) (2) (3) (4) (5) (6) Type 347 Stainless Steel (cont) 53K/52000 59K/12000 29 X C 64K/1000 P.F. 70K/1000 75K/300 30 1600/5 1973 C -.-010 31 1600/5 2764 C 4_.010 32 1600/5 1500 C.010 33 X F 59K/32600 (4) P.F..040 34 P.F. 1811 C 60K/39000 (3).036 35 (Used for calibration of Heat-Eye) (2) I. _ ' -- i ] l ~ -- L I i i i / ' L I I I Ill I I,.....I.I A-10

TEST LOG (cont) Specimen Cross Number Type of Cycle Remarks Number Section of Cycles Failure (1.) (2) (3) (4) (5) (6) Type 347 Stainless Steel (cont) 36 1600/5 1859 C 58K/30000 (1) V P.F. o40 37 1600/5 4635 C (5).40 40 38 A, <21600/5 2114 C T2/2000.025 G 2440 39 1600/5 2440 G Rigid Support (7) V Nozzle No. 3 40 \7 1600/5 3143 G Nozzle No. 4 (8) 41 7) 1600/5 2710 C G 2000 Rigid Support Nozzle No. 3 42 (used for calibration) V_ A-ll1

TEST LOG (cont)... =.........,. / i,. 11 1 i i, i 11. - i i i i i t ' i i. Iiiiii Specimen Cross C 1 Number Type of Se~~~ctinoycles Remarks Number Sedtion ye e of Cycles Failure ( '(2) (3) (4) (5) (6) Tye......, i. _. I. I Type 347 Stainless Steel (cont) 43 (11).025 1600/5 10708 C P Rigid Support Nozzle No. 4 44 < 1600/5 2046 C T2/2000.05 035 V /._ 45 T 1600/5 1956 C T2/2000.025 V ~7 H. S. 21 (vitalli'U~) Cast 1 \07 1500/2.5 1000 C BT 2~o W (l10ol5 3552 C ilml l I c I I I! ' i - l".. -- - I I II I el I1 IT I I I L! 3 A-12

TEST LOG (cont) Specimen Czoss Number Type of Remarks Number Section of CyclesN Failure (1) (2) (3) (4) (5) (6) H. S. 21 (vitallium) Cast (cont) 1700/5 6820 C FC6003 4 \ / (1719).4C6561.049 5 \ / 1800/5 1252 C.045 6 1700/5 1506 C 7 W (1720).o48 8 1800/5 3468 C.047 9 \2/ 1600/5 5305 C ~0375 (1603) 10 I.I ~ I I I I11 A-13

TEST LOG (cont) Specimen Cross NCcles Number Type of Remarks Number Section of Cycles Fail lre (1) (2) ( 3) (4) (5) (6) H. S. 21 (vitallium) Cast (cont) 11 1600/5 17615 C.0o3 16o5 12 777/ 1700/5 7375 T51/1350.o01V 13 1800/5 3902 C / 14 15 1600/5 15334 0.o35 __p ~~~ (1607) 16 1700/5 14489 T51/1350 17 1700/5 3279 C.o.~ (17o8) FC.,oo4 A-14

TEST LOG (cont) Specimen Cross Number Type of Number Section of Cycles Failure (1) (2) (3) (4) (5) (6) H. S. 21 (vitallium) Cast (cont) 19 05 1700/5 10060 T51/1350 20 1800 5 4147 C.0397 21 1600/5 9938 C.036 I 22 1700/5 18411 C T51/1350.0497 - Inconel 1 1500/3 1450 C 2 V.oK15 2 \ 150o/3 2730 C +10/100 3 035 1500/3 428 C BT A-15 HI ' ~ - I - _ - il I II ~ fl I 11 - II I I I l

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (?) (3) (4) (5) (6) Inconel (cont) 4 o1700/5 3167 C T2/500.. 0357 V7< T1/3/1400 5 1700/5 1819 C T2/500 T1/3/1400 6 T 1600/4 7449 C V.035 7.1700/5 706 C T2/,00.035 77 T1/3/1400 8 T 1700/5 2090 C T1/3/1400.025 PTI 79 \ 1700/5 6465 C T2/00 OV.025 10 \0/ 1700/5 3680 C T1/3/1400 03-5 V< -PT10 A-16

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) Inconel (cont) 11 \ 1700/5 2860 C T1/3/1400.028 V, <PT5 12 1700/5 1884 C T1/3/1400.0 30, v C20/1700 13.02E 1700/5 2500 C T1/3/1400 14io 1700/5 2527 C T/3/4oo00 15 1700/5 2804 C T1/3/1400 PTtO 030 V 16 1700/5 3590 C T1/3/1400 17 1700/5 2270 C T1/3/1400 PTI A-17

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) Inconel (cont) 18 1700/5 2576 PC T1/3/1400 3015 C PT5 19.2 / 1700/5 1830 C T1/3/1400..2.025.20 1700/5 2898 C T1/3/1400 21 22 1700/5 4339 FC? T1/3/1400.035 6866 C flex. pipe - ~ — to nozzle 23 1700/5 2250 C T1/3/1400.035 V 24 IIII._ _ I _ I 25 1700/5 3538 FC T1/3/1400 4229 C.035 A-18

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of.Cycles Failure Remarks _(1) (2) (3) (4) (5) (6) Inconel Lot II (1/2' -Inch-Diameter H.R. Rod) 0 47 (Edge) T 1/3/1400 BI 7 (1) 1700/5 2267 C 2 tests on (2) 1700/5 1760 C different 043 - R edges 040 T 1/3/1400 B2 3 (1) 1700/5 2344 C 2 tests on (2) 1700/5 2527 C different 043 R edges B3 1700/5 2622 C T 1/3/1400 047 -- R Crack far B4 2000/5 958- C over usual ending 043 R point. T 1/3/1400 Metallo3B5 2000/5 398 C? graphic examination 039 _ R needed. T 1/3/1400 04 R B7 2000/5 140? C? See. B5 299 T 1/3/1400 046 4 -R Al8a

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks - (.1) (2) (3) (4) (5) (6) Inconel Lot II (1/2 -Inch-Diameter IIH,R.. Rod) (cont) Reproduction B8 1700/5 2560 C Test on New Unit "C" o44 <C T 1/3/1400 B9 1700/5 2283 C do T 1/3/1400 04 C B10.1700/5 2206 C do T 1/3/1400 038 + Bll B12 2000/5.10? C? See- B5 143 T 1/3/1400 043 v R B13 \77 1900/5 580 + C 042 0/,o- o.6 T.1/3/1400 042 R B14 1900/5 463 0? See B5 \04 / ~~~~~~~~T 1/3/1400 044 R A18b

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3)(4) (5) (6) Inconel Lot II (1/2-IEnch-Diaeieter HO.R. Rod) (cont) B15.1900/5 659 C? See B5 T 1/3/1400 B16 1900/5 175 0? See B5 T 1/3/1400 B.17.1800/5 480 0 See B5 V + T 1/3/1400 B318 1800/5 1962 C? See B5 V -— '~/: ~~~T 1/3/1400 Al8c

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) S-816 Alloy (wrought) 1500/4 A o.o8 1 P700 1788 0 N No load 18391 C +100/5108 A P 7+100/10000 1500/4 2 T P1100 2657 F A 0.08 to N 7 V P700 3 v 1700/4 2256 C k4 5 j1700/4 2250 C >V 1600/4 3870 C 6 15o00/4 2630 C 7 1500/4 13280 C A-19

TEST LOG (cont) Specimen Cross Number Type of Numb.er Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) S-816 Alloy (wrought) (cont) 8 1600/4 7497 C 9 \ / 1800/5 1069- C T f1/2150 W L 6/1800 10 1700/5 2426 C T (1/2150 W 1037 V< \16/1800. 03 11 \ /10/5150 C T 1/2150W 1600/5 16/1800 12 1800/5 956' C T J1/2150 W.0388 \16/1800 16/1800 15 7 / 1700/5 1903+ C T j1/2150 W.003 short 14 1800/5 1146' C T j/2150 W A-20

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) S-816 Alloy (wrought) (cont) 15 \K7 1600/4 4600 C T (1/2150 WI I.o36 16/1800 16 7 1600/4 3620 C T 16/1800 Average test temp. was 1615~F 17 1700/5 1956- C T (1/2150 W I 18 1800/5/ 784 C Tl\/62l800 Ji.036 18 1800/5 784 C T {1/2150 WI I.0384 16/1800 19.03457 * 1700/5 2300 C T (1/2150 W\ I 16/1800 o T 1l/2150 W I 20 1600/5 3100' C 16/1800 Average test.0331 temp. was 1660~F \16/1800 21 1700/5 2190 C \. o ( 200~0001700/60 ).032 V< P l200/2? - 000 A-21

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) S.-816 Alloy (wrought) (cont) T (1/2150 \II -16/18o00 22 1700/5 2050 C.035 P L200/23f 4_....6oo.N T fl/2150 ' II 1700/5 t16/180oJ 23 (1685) 1414 C ~.055 P 1200/5f 4 —_ 11.82 N T l/2150 ) I 24 x 1700/5 (1699) 1697 C p 1700/60).038.5 V 100 1040 N 25.034 1700/5 T /21 (1702) 2328 C T 6/1800I 26 1700/5 (1713) 2239 C l/2150 1.36 T t16/1800II 27 1700/5.o035 (1690) 1967 C T i21540I 28 1700/5.0375~ V (1705) 1598 C T /2150 <- - {i/2o16/28ooaI A-22 a

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) s-816 Alloy (wrought) (cont) T ri/2150o1 II t16/0oo0J 29 1700/5 (1695) 1122 C p f7oo/60o l2o 0/05J.~35 2000 N T fl/2150 II 0 1700/5 16/1800ooJ (1700) 2110 C l7oo/6o 2110 C p 11200/237 2000 N T fl/2150 I II 31<~ - / -i 7 0 0 /P5~ t~16/1800f 31 1700//'5 (1702) 1542 C p fL7oo06o ~~~~~.03~~2 C P 11200/23j 2000 N ~~~~~~~~~~~~32~~~ tL16/1800j II 32 \77 1700/5 (1698) 2110- C P t 6 1000 N T r1/2150 ) T L16/18ooJ II 33 1700/5oo (1715) 1700 C P _o___.oD6 ' 4- ~200/22 3121 N T f/2150 II 34 1700/5 6/8 (1719) 1543 C p L200/20 5110 N F/215o II 55 1700/5T 6/8.034 (1700) 2150 C foo/60o. 1200/20 3000 N. ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ i i i 1 i i, i i i. i. A-22 b

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) () (4) (5) (6) N-.155 Alloy (wrought) 1 8838 77 1700/5 3764 FC T f1/3/2200 wI I 3878 c '05 _ )7o/4949 2C,2 74 1700/5 3211 C T fi1/3/2200 W I o/5/14 oof 3 1700/5 3248 C T rl/3/2200 w I.038 5 4i. 77 1800/5 1508 C T fl/3/2200 WI ~03 20/1400 o _~~ ~ ~~ ~: I - - -..... I I l A-22 c

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) N-155 Alloy (wrought). (cont) I~~~~ ~ ~ ~ ~...I.. I l - f l, Il l l l T 1/3/2200 W I 5 /1600/5 3886 0 '50/1400 C.036 Removed for check - ~~~~~~~~~~No crack..o4,o 6\ 1700/5 3105 C T (1/3/2200 W I.03 50/14o00 II l Il _ II. I f l I. I.. I l. I 79\ / 1800/5 1818 C 1/3/2200 W I.042\ /1850/1400.o 8 \ / 1700/5 3195 C T 1/3/2200 W I ~~~~.0439V~~~~~ 650/14oo00 11 1700/5 2052 C T | 1/2200 WI I.034 \ 15/1400 A-23 10 04 V 60o/5 10124 o 5X0 11 /1800/5 2052 C T(//20W *045V ~~~~~~~~~~~~l5/3/200 1~..... _" ', -,..... _...... - ~~A-23.....~.......

TEST LOG (cont) I~~lll I Inl I I J II I I I I I I.. [ I Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5,) (6) II ~ ~ I _ _ ' ' _ I _ll _,_ _ _I~I I I, - _ [ N-155 Alloy (wrought ) ( cont ) -- I II I I l I.... I - l.12.o38K7 1800/5 1228 C T 1/3/2200 50/1400 W) II 13 \1800/5 1095 C T (1/3/2200 W II 13 ' 5/.4oo.048,4 14 1800/5 1042 C T 1/3/2200 W II 5o/1.4oo.035V 15.35< 1800/5 990 C T.1l/3/2200,~~~~0415 V~~~~~ 50/1400 Il l [ 0v 1700/5 2229 - 0X400 } 038, v 16 18oo/5 1130 C T 1/3/2200 W II 18~~~~~~~~~~~~~~~~~~ ~~~~~.o36 V<. ~..~~50/1400.03*5;o, 1700/5 _O95 Cz/2200 WlrI 1? 1700/5 2229 ~ T[ 1/3/2200owI L~~/14oo-0.04v s.8 170/ 195 T 3/2200 w II ~.7oo/~ 1995 c ~ [~/~.14oo.O06 -~ I

TEST LOG (cont) Specimen Cross Number Type of Number Section Cycle of Cycles Failure Remarks (1) (2) (3) (4) (5) (6) N-155 Alloy (wrought) (cont) I. I.,,,,Il 1 l r _ l. _-Il - I II: - - I I _~ 19.0397 1600/5 5153 C T 1/3/2200 150/1400 J II 20 1700/5 2320 c 1/3/2200 WII.0466.-)4 0 / J~ ~ ~ ~ ~~10/ 2i2 C i iTIIii m Ii - I IiIIii_ i- -i, - 21 *043,7i 1600/5 3530 C T 1/3/2200 l 50/1400 wJ II. ~ ~ ~ ~~~~~~ ~ ~~~~~~~~~~~~~ ~~~ ~~~~~~~~~~~~~~~~~~,......'.bE.. M~ m 22 \ / 1600/5 7000 C T (1/3/2200 W-II 50/1400.0417 1600/5 6728 C T |1/3/2200 /50/1400 II III I J..... I I _ - I i i Ill t I 1! -- '! I II I II I I I '~ ~ ~ 13 _ - Ji I - i _l Ill I ]iN] _ - P. A-25

UNIVERSITY OF MICHIGAN 3 9015 03025 140211111111 3II 9015 03025 1402